Safety lowering device



May 23, 1944. G- P, KlMMEL 2,349,735

` SAFETY LOWERING DEVICE Filed June 3, 1940 6 Sheets-Sheet 2 gwoon/kw george RmmeZ www4 May 23g/'1944. G. P. KIMMEL.l i 2,349,735

SAFETY LOWERING DEVICE Filed June 3. 1940 6 Sheets-Sheet 4 4a 4-9 3mm 4george Hffmme May 23, 1944. G. P. lKIMMEI. 2,349,735

SAFETY LOWERING DEVICE Find June s, 1940 e sheets-sheet 5 Geore /l-'zmeZ l SLM , May 23, 1944. G. P. KIMMEL 2,349,735

- SAFETY LowERING DEVICE Filed June s, 1940 e sheets-sheet 6 Patented May 23, 1944- UNITED sTATEs PATENT OFFICE SAFETY LOWERING DEVICE George PL'Kimmel, Brookeville, Md.

Application June 3, 1940, Serial No. 338,643

Claims.

This invention relates to an armor piercing projectile plane.

The invention hereinafter described is constructed on the principle of aiming a weapon at the target or objective so as to make each shot count, as distinguished from the well known method of general distribution of shot, shell and bomb over a specified area in the hope that one or more may hit a vulnerable spot. The invention hereinafter described, instead of depending upon preferably one aerial bomb or torpedo out of a vast number striking a ship or objective to sink or damage the objective, aims to provide a Weapon which may be aimed directly at the objective and which is provided with means whereby the projectile will be more'effective and in the long run Will be less expensive than Where a large `number of bombs or torpedoes are discharged with the hope that one or more of them will reach the particular objective.

In the invention to be hereinafter described, a twin-motor plane is used having the fuselage point constructed of a large calibre explosive shell provided with a time fuse so that the explosion of the shell will occur after the shell has pierced the deck armor of a battleship or other objective. This shell may be a fourteen or sixteen inch shell or larger with the main part of the fuselage enclosing the pilot and to which is also attached the escape mechanism by means of which the pilot may leave the plane suflicient- 1y in advance of the time the shell or projectile strikes the objective so as to be a safe distance away from the explosion.

The escape mechanism includes a detachable parachute and in one instance includes the rear or tail of the plane which latter part is formed of buoyant material so as to form a raft to be used by the pilot when landing on water. The parachute with the oating combined raft and rudder is automatically released and is instantly opened at a predetermined distance away from the objective which may be determined by the pilot.

An object of this invention consists of shooting or diving of a plane in a direct and substantially vertical line and at a speed so great that when the plane and its projectile nose strikes the deck of a battleship or other objective, there will be no question of penetration, no question of the explosion of the projectile within the objective and no question of the total destruction of the objective instead of merely temporarily putting the objective out of commission or action.

Another object of this invention is to provide a powered projectile which is so constructed that it may be flown to an objective, aimed or pointed at the objective, and the operator or pilot released therefrom without changing the flight of the projectile.

A further object of this invention is to provide a powered projectile which is formed with armor piercing characteristics and which is capable of being accurately aimed at an objective.

A still further object ofthis invention is to provide a powered projectile which is formed with supporting Wings and power means carried by the wings, the power means being manually con.- trolled or regulated from a position rearwardly of the projectile.

A further object of this invention is to `provide a dive projectile 1 having an airplane body and guide structure together With an improved escape means for the pilot or operator so that the pilot or operator will be automatically ejected or pulled out of the fuselage by an escape mechanism which is manually controlled by the pilot or operator.

A further object of this invention is to connect an armor piercing projectile to an airplane structure and to ,so form the airplane structure that a portion thereof Will be released from the remaining portion at the time the pilot or operator leaves the airplane, the released portion forming a raft to be used by the pilot or operator when alighting on water. i

A further object of this invention is to form an armor piercing projectile at the forward end of a fuselage, and to cover the rear portion of the fuselage With portions of a parachute, the parachute being attached to the fuselage by a releasable ejecting mechanism which is adapted to at least partially open the parachute prior to the departure of the pilot or operator from the fuselage so as to make certain of Athe opening of the parachute.

A further object of this invention is to provide a combined airplane and projectile and an escape parachute which has the shrouds thereof connected to the pilots seat, `the airplane being formed with a fuselage having an escape track which is operable to force the pilot laterally of the fuselage at the time the pilot leaves the fuselage.

A further object of this invention is to provide in a ying armored piercing projectile structure, a manually releasable escape mechanism initially operable by the pilot or operator so that the projectile may be aimed at the objective, the power controls set or locked and the pilot or operator forcibly ejected from the fuselage.

A further object of this invention is to provide ina vertical or diving position.

Vmounted therein an explosive charge" =I3.

in a powered flying projectile, a separable, buoyant tail part secured to a parachute so that the tail part will float on water and form a raft, the release of the tailV part also assuring the release of the parachute and preventing entanglement of the parachute shrouds with the rear of the fuselage. f

To the foregoing objects and to others which may hereinafter appear, the invention consists of `the novel construction, combination and arrange-y ment of parts as 'will befmore specifically referred to and. illustrated in the accompanying drawings i wherein are shown embodiments of the invention.;

away and in section of an armor piercing projectile plane constructed according to an embodiment of this invention, the plane being shown Figure 2 is a fragmentary longitudinalsection of the rear portion of the fuselage. Figure 3 is aV fragmentary plan view of the rear portionv of the fuselage." Figure 4 is a fragmentary longitudinal section of the forward portion of the fuselage. l

Figure 5 is a fragmentary longitudinal section of the rear portion of the fuselage and the forward portion of the tail structure. Y

Figure 6 is a sectional View taken on the line 6-6 of Figure 3. f y

Figure 7 is a sectional view taken on the line 'I-1 of Figure 3. Y

Figure 8 is a `sectional view taken on thev line 8 8 of Figure 3. f

Figure 9 is a sectionalview taken on the line '-9-9 of Figure 4, showing thev parachute opening means in released or parachute opening position. Figure 10 is a fragmentary front elevation of the parachute clamping or holding bands. f y l Figure 11 is a top plan partlybroken. away an in section of a'modied form of this-invention.-

rFigure 12 is an enlarged fragmentary Vlongituf of the rear portion of the fuselage.- i

Figure 16 is a fragmentary sectional view'taken on the line IS-I Bof Figure 13.

Referring to the drawings and Vfirst to: Figures 1 to 10, inclusive, numeral II] designatesgenerally a fuselage of a plane constructed 'according to an embodiment of this invention and the numeral I I` designates generally a projectile which is formed with the fuselage I Il and projects forwardly thereofk in axial alignment with the axis of the fuselage IB. The fuselage I0 has secured thereto al pair of laterally projecting wings W, and a'pair of motors M are carried by the wings W oniopposite sides-of the projectile I'I-` The motors M have connected therewith propellers P for propelling the planeto the desired objective. I f y The projectile II comprises a`shelll2 which has forward or nose portion of the projectile II 'is formed with a solid'body orfnose I Lhaving a charge firing cap 4I5 mounted on the terminalend thereof. The charge firing cap I5 Iis adapted to be connected to the vchar'fge I3 in* a conventional manner so that whenthe cap I5 strikesit-h ob- 751 jective, the charge I3 will at the proper time be exploded by the firing charge which extends through the body I 4. At the rear of the projectile I I, the fuselage I0 is formed with a pilot chamber and is provided with a cowl which is partly'enclosed by a top wall IS of transparent material and a frontwall I1 which is inclined rearwardly and upwardly from the Iupper surface of the fuselage III. Y

A The cowl formed by the transparent members I6 and. I'I engages over thepilot chamber I8V in which a pilot seat I9 is positioned. The pilot chamber ;I8I at the rear thereof is formed with an opening 420, the purpose for which will be hereinafter described A plurality of radially arranged projectile and plane guiding kns 2i are carried by the fuselage I0 and are disposed about the pilot chamber I8. The fins 2| are of suitable length and width so that when the pilot leaves the plane and locksthe controls thereof, the fins 2| willk coact with the locked controls in guiding the plane and projectile toward the objective.Y The fuselage Il) comprises a substantially solid part 22 enclosing the pilot chamber I8,-the upper portion ofrwhich is formed with the opening 2,0. ,.The'rear or tail portion'of the l fuselage` I0 comprises a plurality of rearwardly extending skeleton framey members or strips 23 which are securedattheir forward ends to the bodyportion ZIJ and extend rearwardly thereof in tapering relation so as to form a rearwardly reducing tail part.v

The skeleton frame-strips`23 rearwardly of the body 2,0 are secured together by means of a plurality of arcuate connecting members'or braces 24 which extendvinwardly of the frame structure so as to provide longitudinal channels 25, thepurpose for which will be hereinafter described.v `At their rear `ends,the longitudinal strips 23 aresecured to an annular ring 26, the strips 23 being welded or `otherwise xedly securedto the. ring 26. A parachute structure generally designated Yas 21 is ladapted to encompass or enclose? the skeleton tail part of the fuselage I which isformed by thelongitudina1 strips 23 and the connecting strips 24 andthe parachute 211s so folded that the loose portions V28` thereof may engage in the channel members V2,4. The remaining portions of the parachute 21 are adapted to be stretched between the frame members 23 so as .toform a substantially solid or smooth wall enclosing the skeleton tail part of the fuselage I0. t Y

The parachute 21 in the present instance is provided on the exterior surfacethereof1 withwa plurality of yieldable bands or strips 29 which are secured to the exterior of the parachute 2,1 in any suitable manner and thesestrips 2,9 are adapted to extend lengthwiseof the fuselage I Il and also provide a means for firmly holding the cover of the parachute against the skeleton frame structure. The stripsV 29 `are ofresilient construction so that when the parachute opensthese strips may bend longitudinally'and in this manner hold the para; chute from collapsing or from undue tearing.

The .body l22 at. the rear thereofA has secured thereto Aa fpair! of vparachute opening springs Y30 which in Figure V-9 are shown in openposition. These springs 30 when the parachute 21 is in inoperat-ive position, are contracted to the position e shown in Figure 6. The skeleton frame` members 23 at a'point rearwardly froms the fuselage lbody member l22, have formed therewith abutments or detents 3I over which the parachute 21- is adapted to engage. The forwarder openend of' tlfie parachute l21! is" lieldf in tight position about thev forward ends of the frame members 23 by means of a forward split clamping band.

The clamping band 32 engages about the strips 29 of the parachute 21 and also the fabric forming the parachute and the rear edge of the clamping band 23 is adapted to engage against the abutments 3| so that the band 32 will not slip rearwardly under vibration or the like. The free ends of the band 32 are formed with band locking ears 34 and 35 which are provided with openings 36 and 31 relatively. A band locking member 38 engages through the openings 36 and 31 and is adapted to tightly hold the band 32 about the parachute and about the skeleton frame structure formed by the longitudinal strips 23. The locking member 38v extends lengthwise of the fuselage |8, and, as will be hereinafter described, is adapted to be moved forwardly to a band releasing position. l

A plurality of intermediate clamping bands 39, 49 and 4| are mounted about the parachute 21 and are constructed similar to the band 23, the band 39 having ears 42 and 43 which are held in locked position by means of a releasable locking member 44. The band 40 is provided with a pair of ears 45 and 46 which are held in locking position by means of a locking member 41, The band 4| is provided with a pair of ears 48 and 49 which are held together by means of a locking member D. An elongated releasing rod 5I is secured to the locking members 38, 44, 41. and 50 and extends beneath the fuselage I0, terminating at a point forwardly of the rear end of the body part 22.

A releasing lever 52 is pivotally mounted on a pivot 53 carried by a notched or toothed plate 54 which is mounted within the pilot compartment I8. The lever 52 is provided with a spring pressed latching dog 55 which is connected to a dog re leasing lever 56 carried by the upper end of the lever 52. The dog `55 is adapted to engage in a selected notch 51 carried by the plate or rack 54 so as to hold the lever 52 in a normally band locking position. The forward end of the rod 5| is connected to the lower end of the lever 52 being connected to the lever 52 by a connector 58 which is slidable in a slot 59. The lever 52 at its lower end extends through an opening 60 which is formed in the bottom of the body 22.

The shrouds 6| of the parachute 21 are secured to the pilot seat I9, the shrouds 6| being connected to fastening devices 62 which are fixed to the seat |9 in such a manner that when the parachute 21 is released from the fuselage I0, the seat I9 will be maintained in a normal upright position. The legs 63 of the seat |9 are each formed with openings 64 through which seat locking members 65 engage. The locking members 65 are connected to the rod 5| by means of connecting members 66 which may be integral with the locking members 65. The locking members 65 and the connecting members 66 may be constructed in the form of an L-shaped locking structure having one leg 65 thereof engaging in the openings 64 of the legs 63 and the legs 66 may be extended through openings 61 formed in the body 22,

A rear clamping band 68 engages about the parachute 21 and the bands 29 and the rear clamping band 68 is provided with a pair of ears 69 and 10. A locking member 1| engages through the ears 69 and 10 and is fixed to the releasing rod 5U. In practice the locking members 44, 41, 50 and 1| are constructed of such a length that these locking members are disengaged from the clamping membersin progression from the rear toward the front so that when the foremost band locking member 38 isreleased so as to permit the parachute opening springs 39 to open the parachute, there will not be any band rearwardly of the forward band 32 which will prevent the instantaneous opening of the parachute. I

A tail structure 12 is carried by the rear end of the fuselage I8 and this tail structure 12 com-4 prises a substantially stationary forward body part 13 and elevators 14 which are pivotally connected to the rear of the body part 13. The elevators 14 are operated by conventional operating means extending through the fuselage and the tail structure 1,2 also includes one or more rudders 15 which are pivotally mounted on the body Ypart 13. The rudders 15 are adapted to be operated in the conventional manner and prefer.

ably by releasable means so that when thevtail structure 15 is released from the fuselage by opening of the parachute 21, the operating connections to the tail structure 12 will also be disconnected. 1

The tail structure 12 is detachably connected to the fuselage l0 by means ofl a plurality of spring arms 16 which are fixed to the body part 13. The spring arms 16 at their forward ends engage about `the rear part of the fuselage l0 and are formed with releasable hooks or lugs 11. The bands 29 of the parachute are each formed with a detent or lug 18 which is adapted to be engaged by the hook or locking member 11 so as to detachably lock the spring fingers 16 on the rear of the fuselage ID. The rear ends of the parachute reinforcing members 29 are connected to a plate 1.9 which forms the top of the parachute 21 and the forward end of the tail member 12 may be connected to the plate 19 by means of connecting members B0. The body part 13 of the tail member 12 is preferably hollow for atleast a portion thereof so that the tail member 12 will be buoyant. A pilot parachute 8| is disposed within the body part 13 of the tail 12 and preferably the body part 13 is provided with a spring pressed closure 82 through which the pilot parachute 8| is adapted to be ejected.

A pilot parachute ejecting spring 83 is disposed within the body 13 and the rear end of the spring 83 has secured thereto a follower or plate 84. The forward end of the spring 83 engages against a plate or abutment 85 formed in the body '|3 as shown in Figure' 5. The spring 83 is held in a compressed position by means of a pivoted locking member 88 which is mounted on a pivot 81. The locking member 85 has one portion thereof projecting within the body part 13 and is adapted to engage against the rear side of the follower 84. The projecting portion of the locking member 88 is provided with an opening 88 through which a locking member 89 engages. The locking member 89 is formed in substantially L-shape with one leg 98 thereof extending at right angles from the body 13 and this leg 9|) is connected to the rear end of the releasing rod 5|.

The tension of the spring 83 tends to hold the projecting end of the locking member 86 against the angle formed between the two parts 89 and 90 of the locking member and preferably the locking part 89 is substantially shorter in length than the locking member 1| so that the locking member 89 will be released before the locking member 1| is released from the band ears 69 and 1.0.

In order to provide a means whereby the pilot seat I9 may be discharged from the fuselage I8 in a lateral direction, I have provided a pair of seat guiding tracks 9| which are secured to the the: shrouds IIv pullA the-seat I9 rearwardly;l the seat.` |9f-with .the Jpilot strapped theretoryvillv be.I

pulled i rearwardly Y and f 'outwardly .of the. Yskeleton tail part of the fuselage f'III so;.that-theshrouds ,6 I

will not become entangled in any-.parto the fuselage and so .thatthef pilot .-,se'at :with Vthe fpilot.

strapped theretonwillabe pulled iclear fof the supporting bars.l 92. land i931 which extend trans.-

versely across the skeletoniof the-fuselage, .the

track supporting `members i 9.2 and; 93 being. Vfired topairs of-frarnemembers 23; Y,

Referring now'. toeV Figures 1.1; .to

asesinas frame members. 2.3 .1 and extend. rearwardly. .and upwardly. When the parachute# 21opens aridiz gage inV afslot |24.v formed in theforward sides of' the Afrontlegsz,IZIMQ.'l'herear-legs l|2| are substantially.,shorterain. length than the front legs 20,1` so 'thatthe seat ||11Will be disposed in a normal. upright position when the, seat I1 is in. its

thereis disclosed :'hereina modified form of'this invention which is' adapted for use on land ob-jeCf tives..- An armorfpiercing projectile v94 is formed at .the forward. end ofa fuselage-.95,and the pro-V jectile AA94 comprises ,a' hollow body 961having a; solid nose 91 terminating in a firing cap 9,8. A charge 99- isdisposed in' the body 96 andarear wall is connected to the bodyt and,v is of such a constructiony that .it may bei removed for the purposeof inserting the explosivercharge 99.'

Apair of-wings vlill arecarried by the.=fuselage 95 and partly by the-projectile bodyg and a` pair of lmotors v|02 varel carried one `by Veachwing |9If.

vThe. motors |02 `are controlled by suitable ccntrolling devices extending into the pilotcharnber.

|03 formed in lthe fuselage 95., A tail structure |041 is carriedV by-the rear ofthe fuselage 95 and elevators |05 are pivotally cyarriedby the real-of the stationary partlliof. the tail structure |04. Adepending rudder structure |01'is carried by the tail structure |04 and it will `be understood that the pivoted part |08 of the tail structure |91 andthe elevators |05 are connected vin a conventional manner to Control devices `extended into the pilot chamber |03. i; Y A parachute housingi I09jis carried bythe .fuselage 95 and in thepresent instance the `housing |09, is substantially elliptical in, transverse sec-f tion and is inclined upwardly and rearwardly and opens through thev upperfsidei-.of the fuselage 95.*4A closure plate ||0 engages therupperppen end of thehousing` |"09f and*is releasably held in the open upper end of the housinglii)l by means of a plurality :of clamping membersIIL The clampingfmembers IIIwarein the forni of spring clips which are fixed to\fthe closure ||0 and normally holdtheclosure I I0 in an operative position to close the upper end of the housing I0 E). A parachute ,I-|.2 isglnountedrin the-housing l|09 and the shrouds :|.I3yof -thefparachute II2. .are

V| I8 in the upperside thereof through which the pilot seat I |1-,withlthe pilot strapped thereto is adapted to bevpullead. Apair-,of longitudinalarcuu ate chair `guiding 1 tracks AI1|9 `.are carri-edby the fuselage 9,5 and extendupwardlyand rearwardly. These tracks IIJ9, are. preferablyot substantially U- shape transverse `sectionv and the le gs7|20`` andV |2| of :the 4seat ||1 looselywengage withinwthe channel trackrmembers H9.,y Each track member p |,I9Mat itsforward orinner endis formed. with 'IlorrnalpositionV 1'; Y

-The parachute, I IZfpi'siadapted to be ejected from.` the Yhousingyliiby; means of an expansive spring or. charge member which is disposed in thehousing',|09f'120neendfof the spring |25 bears against'the innerfwallor bottom] 26 ofthe housing,|09 and.agfollower g orcap |21 engages the other or upperend of the springy |25. yThe cap or follower |21- Vis slidable fin the `housing |09 Yand bears againstfthe parachutel I2.. y Thev spring |25 is; held-ina compressed positionby means oi a pivoted latch member |28'which is mounted on a pivot |29. :The lpivot|729 extends through a pair of,ears|30 carriedibyvtheufforward side of the housing |09andthe, bill `of* the latch'mernber |28 is 'adaptedto engage'in an" opening |31 formed in the` forward sidegof the housing |09.` I

The latchvmember@ |28V engages` against the upper -side of the fo1lower |21 so asto normally holdthefspring |25 ina compressed position. A spring |32 is interposed 'between the housing |09 andzthelatch releasing-lever |33 which-is formed with the latch. |.28 so aste constantly and yieldably holdthe latch |28 ina locked position.

.Alatch releasing lever |34 is pivotally mounted on a pivot |35A carried by a bearing |36 which is fixed to the fuselageA 95. The' releasing lever. |34 is connected to ythe latch lever |33 by means of a c'onnecting'link` |31. The releasing lever |34 is held in; aglatch locking position by means of a toothed rack or quadrantY |38, the lever |34 having a springpressed pawl .lllconnected to a pawl releasinglever. |40. The pawl |39 is adaptedl to engage theouadrant|38`andthus hold the leverf 34=in a latch locking position.

; In `order to provide av means whereby the scat |,|,1= may beheld; in a. .1"lxed or locked` position, l

and wherebytheseatgl |1'may be released when the latch II 2,8 is released, I have provided a pair of pivoted seatslockingrarmsv'i 40 which are pivotally carried by bearings |4I iixed to thefuselageg.

The ,seat lockingfarmsV |40 arejs'pring pressed to" vinthe position .showninligures l2 and 13 and inthis positionthe seat. locking levers or arms |49, will be engaged 1in the notches or keepers |43. The bar |44 will constantly ,press the seat ||1 forwardly; but .the` forward tilting of the seat I|1is preyentedbyengagement of the seat locking levers |40 inthe notches |43.

In order to providea means whereby the' shrouds ,I Igfandthe parachute I I2 will not bei comerentangledwithdthe tail structure |04, I have provided a plurality l of. guardmembers intheform'of. tensione'd wiresor rods which are connectedat theirforwardends to the fuselage 95, and, are Connbgd at.. their-rear ends to the upper surface u ofV V, theI :stationaryU tail part IIJI. Theseguardinembers .|r lform a `screen about the upper part of the tail structure |04 so that the shrouds 3 will not become entangledwith the tail structure |04. I A

The fuselage 95 is provided with a transparent connector |46 formed by an upwardly and rearand the sighting member |49 'is disposed in a position with the longitudinal axisV thereof parallel with the longitudinal `axis of the fuselage 95 and the projectile. 94.

In the use and operation of this weapon shown in Figures l to 10, inclusive, the plane structure will be operated in a conventional manner by the pilot strapped to the seat |9. When the pilot nears the objective which in the present instance may be a oating objective such as a battleship or the like, the pilot will sight the `projectile through a sighting member |5I which is carried by the cowl |6-|1. The plane is disposed in either a vertical Idiving position or a diving position inclined to the vertical and the pilot initially locks the normal controllng mechanism for the plane and operates the motors M at their fullest speed so that the plane will be moving at the highest possible speed.

With the controls for the motors M and the plane operating structure locked, the pilot pulls the parachute releasing lever 52 rearwardly to its released position. Rearward movement of the lever 52 will pull the releasing rod 5| forwardly and progressively release the parachute clamping bands 68, 4|, 40, 39 and 32 and will also release the parachute locking lever 8B. When the parachute locking lever 86 is released, the spring 83 will expand and force the parachute 8| outwardly of the tail member 13, swinging the spring pressed closure 82 to an open position. The shrouds |52 of the parachute 8| are connected to the body part 13 so that the small parachute 8| will substantialy support the tail part 12 above the main parachute 21.

When the foremost parachute clamping band 32 has been released, the parachute opening members will raise the forward open end of the parachute 21 to permit the air to enter within the parachute 21 and thus pull the parachute 21 from the skeleton fuselage members 23. As the parachute 21 tightens on the shrouds 6|, these shrouds will pull the seat I9 rearwardly and laterally along the tracks 9| so that the pilot will be supported from the parachute 21.

The parachute clamping bands 32, 39, 40, 4| and 68 may drop on the ground or in the water, these bands being of such resiliency that as soon as they are released they will snap away from the parachute 21. As the motors M of lthe plane are at this time operating at their full speed and the ailerons are locked relative to the wings W, the main body of the plane will move in a substantially straight line toward the objective.

In order to assist in maintaining the plane in a straight line, the ns 2| will be active, the fins 2| serving as a supplemental fixed rudder structure for guiding the projectile and the plane toward the objective.

When the projectile strikes the objective, the projectile will pierce the objective and the charge I3 will explode after the piercing of the objective'through the charge firing mechanism connected to the cap I5; As the pilot has left the plane and is floating downwardly with a parachute 21, the pilot will have a fair chance of surviving afterthe explosion of the projectile The tail structure 12 being formed of buoyant material may be'used bythe pilot in floating on the water.

Where the structure shown in Figures 11 to 16 is used, the pilot will point the projectile 94 toward the objective and lock the controls for the motors |02 and the controls for the rudder structure |04 together with the conventional ailerons or other controls.V The projectile 94 will rbe pointed directly at the objective which will be sighted through the sighting member |49. After the controls for theairplane have been locked, the pilotmay pull the releasing lever |04 rearwardly so as to release the spring |25 from the latch |28.

Release of the spring 25 will permit this spring to expand and force the closure ||0 from the upper end of the parachute housing |09. At the same time the parachute ||2 will be ejected from the housing |09 and with the opening of the parachute 2, the pilotI `seat |1 will be pulled from the fuselage 95. At the same time that the latch |28 `is moved to a released position, the seat locking arms |40 are released by rearward movement of the locking bar |44 thus permitting the spring pressed locking levers |40 to swing rearwardly to a released position. When the parachute l|2 opens the seat ||1 is pulled outwardly and upwardly along the tracks l I9 and the guard members |45 will prevent any of the shrouds ||3 from becoming entangled with the rudder or tail structure |04.

With a weapon constructed according to this invention, the objective can be hit more accurately than where a bomb or torpedo is released from a bombing plane and permitted to gravitatingly drop downwardly onto the objective. With a structure of this kind, the projectile is pointed at and moving downwardly in the direction of the objective before the pilot leaves the plane and as the controls for the plane are locked, the plane will not vary in its direction toward the objective. As the objective for a weapon of this type has a value far greater than the cost of this weapon, the use of this weapon in destroying the objective will not be out of proportion to the results obtained thereby.

In order to provide a means whereby the wings W or |0| may be released from the projectile, a suitable shear may be placed adjacent each bolt securing the wings to the projectile and fuselage so that the initial impact of the projectile will cut the bolts and release the wings from the projectile. In this manner the wings will not impede the piercing of the objective by the projectile. This same result may also be obtained by providing frangible bolts wherever practicable.

What I claim is:

1. In a plane structure including a fuselage and wings; said fuselage including a skeleton rear portion, a combined skeleton cover and parachute, means releasably holding said cover and parachute on said skeleton rear portion, a manual operator connected to said holding means, a buoyant member connected to said parachute and operatively connected with said holding means, a supplemental parachute carried by said buoyant member, and means for releasing said' supplemental. parachute coinciy dent with the release of, said parachute.

VIn 'a Vplane `struct-,ure including a fuselage and fwings; said fuselage including'askeleton rearfiportioln, a, combined skeleton cover ,and

eparachuta means releasably kholding said *cover andfparachute on said .skeletonrear portion, a manual operatorconnectedl to said ,holding mea-ns; va buoyant lmember)connected tosaid parachute and operatively Iconnected with said holding means, a lsupplemental. parachute carvried by said buoyant member, an ejector for said supplemental parachute, andrneans connected with said holding means, for rendering said ejector active upon release of said holding means.

In a plane structureV includingA wings and a fuselage; said fuselage includingy a skeleton rear portion, a combined parachute and cover nabout :said 'skeleton rear portion, circular resilient split a Apilot seat track in said'fuselage, a pilot-seat on saidtrack connected to said parachute, locking Vmeans for locking lsaid 'seat relative to said `nach and means connecting said locking means withpsaidxoperator. Y y

4. In an aircraft having Wings and a power means carried Aby `said Wings, a skeleton fuselage, a parachute substantially enclosing at least a portion of said fuselage,. a pilot seat connected to said parachute,- releasable holding'means` for `holding saidparachute on said fuselage, a hollow rblloyanttailassembly releasab-lysecured to said fuselage, a parachute for said tail assembly,.-and

vmeansrconnected with said vholdingmeans for releasing said second vparachute Vcoincident withV said vfirst parachute. l a

- ,5. In an aircraft vhaving a fuselage and wings, power means carried by said wings, a detachable hollowbuoyant .tail lstructure attherear of said fuselage, a parachute at least partially enclosing said fuselage, releasable clamping means holding `said. parachute and said tail structure on said fusela'ge, a pilot seat connected to said parachute,

meansreleasably holding said seat in said fuselage, said V`clamping means including forwardly projecting resilient hook members carried e by said tail, keeper means carried by said fuselage, .and afsplitv clamping band holding saidk hook members in ,engagement with said keeper means, and a singlereleasing mechanism forsaid clamping ,means `and .said seat holding means.

` GEORGE P. RIMMEL. 

